Figs.3 & 4 N.A.CA. Technical Memorandum Kb.355 N iH -H JO Pj +» CD O :0 -P Down 2(tall h3avy)4° 5 2° rH CO ch. ■ Up .0 °(nose heavy) CD nO 60 80 100 120 *4 Airspeed of airplane,M.P.H. A = Power on,engine upright. Thrust line 7in.below e.g. B = Calculated curve,power on, thrust line through the e.g.… … Airspeed of airplane Ratio= Maximum horizontal airspeed Fig.4 Eng. Div. CO.-6 airplane. Apparent increase in downwash due to the slipstream.
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